Aeroplane.



C. A. TEFFT.

AEROPLANE. APPLICATION FILED APR-22, ISIS.

LWWWW PamntedAug. 29,1916.

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4 TTOR/I/EYS C. A. TEFFT.

AEROPLANE.

' APPLICATION FILED APR-22' I916- Lfl figfiu Patented Aug. 29,1916.

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WITNESSES wmvron w/M;M/ W BY.

Q1? 27M A A TTORNEYS CLINTON A. TEFJET, 0F GLOVERSVILLJE, NEW YORK.

AEEOJPLANE.

trac ea.

Specification of Letters Patent.

Patented Aug. 2%, Twit.

Application filed April 22, 1916. Serial No. 98,01t.

To all whom it may concern:

State of New York, have invented-a new and Improved Aeroplane, of which the following is a full, clear, and exact description.

This invention relates to airships and particularly to an airship which combines the buoyancyof a" dirigible balloon and the characteristics of an aeroplane.

The object in view is to provide an improved construction which will be satein use and which will have a large carrying capacity without straining any parts of the machine.

Another object in view is to provide a construction which will have substantially the speed of an aeroplane and the usual characteristics of such a machine, and in addition the buoyancy which will prevent falling in case of trouble with the engine or other parts of the machine.

A still further object in view is to provide an aeroplane construction with hollow lanes merging into a substantially tubular ody extending an appreciable distance to the rear, the hollow part of the planes and the body being arranged to receive a light gas for producing a buoyant efiect.

In the accompanying drawings: Figure 1 is a side view of a device embodying the invention, certain parts being broken away for better illustrating the construction. Fig. 2 is a top plan view of-the structure shown in Fig. 1, part being broken away for showing the interior structure of certain parts ofthe machine. Fig. 3 isa front-view of the structure shown in Fig. 1. Fig. 4: is a rear view of the structure shown in Fig. 1.

Referring to the accompanying drawings by numerals, 1 indicates the body of the machine to which suitable traction and supporting means 2 are secured, said traction and supporting means including suitable braces and also wheels. Associated with the 'body 1 is a driving engine and other usual parts of an aeroplane whereby the propeller 3 is rotated and the steering mechanism is operated, these parts, however, not being shown as the detail structure thereof. forms no part of the present invention. Tn connectionwith the steerin mechanism it may be stated that instead 0 having the conventional steering now commonly in use the steering mechanism is connected with the rudder 4 for steering the aeroplane laterally or in a horizontal plane,-and also-connected to the plane or rudder 5 for steering up and down.

The frame 1 may be of any suitable structure and may be inclosed if desired, the same being connected to a lifting plane 6 which extends an appreciable distance on each side of the frame 1, as shown in Fig. 2, said lifting plane being formed of the usual shape on the lower side while the upper side isrounded so as to produce an open chamber in which gas may be inserted. Suitable braces 7 may be provided for holding or supporting the covering, which covering may be of any suitable material, as for instance, sheet aluminum. Connected with the lifting plane 6 is a tubular member 8 which is normally held in a certain position by suitable ribs 9 and which is designed to receive a light gas so as to produce a buoyant efiect for assisting the buoyant efl'ect produced by the light gas in the lifting plane. The lifting plane 6 and the tubular member 8 may be connected up so that the gases will mix or may be divided as preferred so that in case one art gets punctured the other part will still be retained.

The member 8 is rounded and constructed substantially on the stream line efiect,

. and the enlarged part of the plane 6 is arranged almost directly in back of the operating face when the machine is in use so that there will be little additional resistance to the air caused by the use of these members which carry the lifting gas. These members are not collapsible but are maintained in -their position bythe ribs 7 and -9=and other bracing members it the same are found necessary. Of course, the device may be made of any-size and the width of the lift ing plane 6 may be varied as desired as well as member 8, but it is desirable to have these members suficiently large to contain a light gas of sufficient volume to support the device together with the pilot in the air in case the engine should brea down or any other similalff iticcident should occur, thus preventing a a In operation, when it is desired to use the aeroplane hydrogen or other light gas is forced, into the lifting plane 6 and also into member 8 until the proper quantity has been inserted. This will produce a buoyant efi'ect and if these members are of sufficient size it will cause the machine to rise unless anup any small leakage.

gradually descend. If

chored or provided with a load. Preferably the parts are so proportioned as to causethe' device to remain suspended in the air with one of two persons thereon whereby the fo'rmovement and the lifting of any additional load would necessitate. the operation ward of the engine in the usual manner. If desired, a small gas could becarried for producing gas to take In the practical operation of the device it'is aimed to maintain the engine and other parts in proper condition for operation and also to maintain the gas in the for any reason the engme and associated parts get out of order the device could not fall and will either remain in the air or will there is enough gas to old the device in the air the repairs-can be made while in'the air. After th made a landing is also made asquickly as .possible and the complete permanent repairs sible in vide for ,taining the device inthe provided for before becoming torn or the device would remain suspenda landing is. preferably made as soon as posorder to repair a new supply of lifting gas. In this wa the aviator and passengers will be reasona 1y secure against accident, as two independent means are provided for maindevice has become inoperative the other described, a hft per and lower face,

manufacturing device and lower faces, lifting plane and member 8. If

further use of the de- .vice. In case the gas should escape by reason of part of the envelop otherwise,

' by reason of the aeroplane structure, but

the parts and pro-- air and when either vice is utilized for making safety.

What I claim is:

1. In. an aeroplane of the character deing plane formed with an upsaid upper face diverging toward the rear from the lower face whereby a comparatively large space is produced between said faces designed to-receive a lifting gas, and a container extending rear- ,wardly from said lifting plane, the top and bottom walls of which merge into the upper respectively, of said lifting plane, said container being'arranged to receive a liftin gas whereby the aeroplane is given a certain buoyancy.

2. In an aeroplane of the character described, a lifting plane formed of two wings,

CLINTON A. TEFFT.

Armin; L. GRAFF, ALVA-n G. VAN HEUSEN.

the landing in Sand planes at the point of 

